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Method for generating inner surface of wing panel

A technology of inner surface and curved surface, which is applied in the field of inner shape and surface generation of wing panels, can solve the problems of non-uniformity, cumbersome and time-consuming, and achieve the effect of improving efficiency and accuracy.

Active Publication Date: 2020-01-14
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Purpose of the invention: To solve the current inconsistent, cumbersome and time-consuming modeling problems, propose a method for generating the inner surface of the wing panel

Method used

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  • Method for generating inner surface of wing panel
  • Method for generating inner surface of wing panel

Examples

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Embodiment 1

[0022] The following takes the ARJ21 aircraft as an example to illustrate the specific application process of this method.

[0023] The ARJ21 wing is a hyperboloid airfoil, and the thickness data of the inner surface changes linearly along the span direction, so the forming method of the first step is adopted.

[0024] For each linearly changing surface block between the two long girders of ARJ21, a thickness line is established at the boundary along the normal direction of the shape, and then the thickness line is used as the boundary, and the shape surface is used as a guide to create the inner surface boundary line and Guide line, and then create an inner surface based on the boundary line of the inner surface and the guide line. According to the above principles, the inner surface of each linear change area is created. The complete curved surface from the wing root to the wing tip between the two long stringers is spliced ​​by these inner surface blocks, such as figure 1...

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PUM

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Abstract

The invention discloses a generation method of an inner model curve face of a wing wall panel; the inner model data of the wall board is stored in Excel format by a self-defined format; through original data, accurate wall board, beam, and long truss inner model face are formed rapidly according to appointed method; when the wing appearance is a ruled surface or a dual-curve face, and the thickness of the inner model face between every two long trusses is changed linearly along an expanding direction, the inner model curve face of wing wall panel is generated by step one; when the wing appearance is a ruled surface or a dual-curve face, and the thickness of the inner model face between every two long trusses is changed nonlinearly along the expanding direction, the inner model curve face of wing wall panel is generated by step two; when the thickness of the inner model face is nonlinearly changed along the ruled surface or the dual-curve face, the inner model curve face of the wing wall board is generated by step three. The method greatly improves the molding efficiency and precision of the inner model of the wall board.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure modeling, and in particular relates to a method for generating an inner curved surface of a wing wall plate. Background technique [0002] At present, there are many types of domestic aircraft, and the inner shape of the wing panels is becoming more and more complex. Generally, manual modeling or programming is used for a specific model to solve the problem. The disadvantages of this method are: there is no unified standard for design, and the internal shape errors caused by different personnel and different modeling methods are also different. The update is also very cumbersome and time-consuming. New models still need to be manually or reprogrammed to model. Contents of the invention [0003] Purpose of the invention: To solve the current inconsistent, cumbersome and time-consuming modeling problems, a method for generating the inner surface of the wing panel is proposed. [0004] ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/23
CPCG06F30/15G06F30/20
Inventor 史劲松
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA